Aircraft engine equipment forming an engine access hatch

Abstract

The invention relates to aircraft equipment of the type comprising power electronic elements, said equipment being intended to be mounted on an aircraft engine casing (9), around an engine compartment. It constitutes a closing hatch for an opening (10) made in the casing. Figure for the abstract: Fig 3

Description

Title of the invention: Aircraft engine equipment forming an engine access hatch technical field

[0001] The present invention relates to aircraft engines and more particularly to equipment which is mounted or intended to be mounted on an engine casing.

[0002] The invention relates more particularly to an aircraft turbomachine having a casing with an opening allowing access to the internal volume of the turbomachine in order to carry out the installation or configuration of the machine. Previous techniques

[0003] The turbomachines are equipped with a casing located in the nacelle, this casing having openings fitted with access hatches which allow access to the internal compartments of the engine during installation and configuration and to close the casing during normal operation of the turbomachine.

[0004] Turbomachines are also equipped with various types of equipment that perform various types of functions, which are mounted on the casing in order to optimize space in the engine compartment.

[0005] In an advantageous application of the invention, the equipment includes power electronic elements which are mounted on the casing of the intermediate section of an aircraft engine, at the level of the low-pressure compressor.

[0006] With reference to Figures 1 and 2, which depict an internal casing 1 of an aircraft engine equipped with an opening 2 closed by an access hatch 3, it can be seen that the equipment 4, mounted on supports such as 5, must generally be offset from the access hatch so as to allow access to the internal engine compartment without having to remove the equipment. This solution is disadvantageous in that it results in a loss of space on the casing ([Fig. 1]).

[0007] When the equipment 4 partially covers the access hatch, the loss of space is reduced ([Fig. 2]). However, during maintenance operations, it is necessary to disconnect the electrical power harnesses and the various conduits of the equipment, and then remove the equipment before opening the access hatch 3. Description of the invention

[0008] In view of the foregoing, the object of the invention is to overcome the aforementioned disadvantages by optimizing the installation of equipment in the engine compartment of an aircraft, while combining the advantages of compactness and ease of implementation.

[0009] The invention therefore relates to aircraft equipment of the type comprising electronic power elements, said equipment being intended to be mounted on an aircraft engine casing around an engine compartment, this equipment constituting a closing hatch for an opening made in the casing.

[0010] Thus, the equipment is mounted directly onto the hatch, which optimizes the space around the housing. Furthermore, it is not necessary to remove the equipment before opening the hatch.

[0011] For example, a compressor is placed in the engine compartment.

[0012] According to another feature, the equipment includes means for fixing the equipment to the housing, including a sealing gasket.

[0013] Advantageously, the equipment includes a set of cooling fins intended to extend into the engine casing, in heat exchange relationship with an airflow from the engine.

[0014] According to yet another feature of the equipment according to the invention, said airflow is a secondary airflow of the engine.

[0015] The invention also relates to an aircraft engine comprising a retention casing with an access opening, this engine comprising at least one piece of equipment as defined above mounted on the casing, in the access opening.

[0016] According to another feature, the equipment is mounted on an outer face of the housing, with cooling fins extending into the housing, in heat exchange relationship with an airflow from the engine.

[0017] In one embodiment, the equipment is a power management box for an electric defrosting system. Brief description of the drawings

[0018] Other objects, features and advantages of the invention will become apparent from the following description, given solely by way of non-limiting example, and made with reference to the accompanying drawings in which: - Figures [Fig. 1] and [Fig. 2], which have already been mentioned, illustrate solutions installation of equipment on the crankcase of an aircraft engine according to the state of the art, and; - Fig. 3 illustrates an embodiment of aircraft equipment according to the invention. Detailed description

[0019] Figure 3 shows the midsection of an aircraft engine, in which the nacelle 6, the axis of rotation X-X' of the engine, and the low-pressure compressor 7 of the engine, located in a casing 8 of a compartment 20 of the engine, are recognizable. the whole being arranged inside a retention casing 9 placed between the nacelle 6 and the casing of the low pressure compressor 8.

[0020] The containment housing 9 has an opening 10 which coincides with an opening 11 having a shutter 12 allowing access to the low-pressure compressor from outside the containment housing 9 during installation and maintenance operations.

[0021] The motor here is provided with equipment 13 fixed to the retention housing 9.

[0022] In an advantageous embodiment, the equipment 13 consists of a control unit incorporating power transistors designed to provide an electric defrosting function by joule effect.

[0023] As can be seen in [Fig.3], the equipment 13 constitutes a closing hatch for the opening 10. In other words, it incorporates in its structure an extension that attaches to the retention casing.

[0024] It thus comprises, in the lower part, i.e. in the area facing the casing 9, peripheral shoulders 14 intended for fixing the equipment to the casing 9 by screwing into inserts 15, with interposition of sealing gaskets 16.

[0025] As can be seen, the equipment 16 is mounted on an external face 17 of the housing facing the nacelle 6 and here includes a protruding part 18 which fits into the opening 10.

[0026] On the opposite side, on the inner side of the retention housing 9, the equipment 13 includes a set of cooling fins 19 extending parallel to the axis X-X' and extending in projection between the retention housing 9 and the housing of the low-pressure compressor 8, in thermal exchange relationship with a flow F of the engine.

[0027] As can be conceived, the invention which has just been described, in which the access hatch is integrated into a lower area of ​​the equipment, requires only a disconnection of the electrical harnesses and / or the piping of the equipment, then an unscrewing of the hatch to access the inside of the motor.

[0028] In addition, positioning the equipment at the opening allows for a gain in surface area on the housing.

[0029] It is advantageous to provide bosses at the location of the installation of the inserts in the housing.

[0030] Advantageously, the seal 16 is a flat elastomer seal which is inserted in compression between a boss of the housing and the equipment.

[0031] As previously stated, the presence of the cooling fins allows the equipment to be cooled.

[0032] Furthermore, the equipment is mounted at the low-pressure compressor, in the so-called mid-fan section of the engine. Therefore, there are no blades in the vein located between the retention casing 9 and the casing 8 of the low pressure compressor which could otherwise interfere with the installation of the fins.

Claims

Demands

1. Aircraft equipment of the type comprising power electronic elements, said equipment being intended to be mounted on a casing (9) of an aircraft engine, around an engine compartment, characterized in that it constitutes a closing hatch for an opening (10) made in the casing.

2. Equipment according to claim 1, in which a compressor (7) is placed in the engine compartment.

3. Equipment according to claim 1 or 2, comprising means for fixing the equipment to the housing including a sealing gasket (16).

4. Equipment according to any one of claims 1 to 3, comprising a set of cooling fins (19) intended to extend into the crankcase, in heat exchange relationship with an airflow from the engine.

5. Equipment according to claim 3, wherein said airflow is a secondary airflow from the engine.

6. Aircraft engine, comprising a casing with an access opening, characterized in that it includes equipment according to any one of claims 1 to 5, mounted on the casing in the access opening.

7. Aircraft engine according to claim 6, in which the equipment is mounted on an external face of the casing, cooling fins (16) extending into the casing (9) in heat exchange relationship with an airflow (F) from the engine.

8. Aircraft engine according to any one of claims 6 and 7, wherein the equipment is a power management box for an electric de-icing system.

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